CN116745546A - Dual drive redundant load transmission and method - Google Patents
Dual drive redundant load transmission and method Download PDFInfo
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- CN116745546A CN116745546A CN202180087788.2A CN202180087788A CN116745546A CN 116745546 A CN116745546 A CN 116745546A CN 202180087788 A CN202180087788 A CN 202180087788A CN 116745546 A CN116745546 A CN 116745546A
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- load transmission
- input shaft
- coupling assembly
- redundant load
- drive
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- 230000005540 biological transmission Effects 0.000 title claims abstract description 99
- 238000000034 method Methods 0.000 title description 9
- 230000009977 dual effect Effects 0.000 title description 2
- 230000008878 coupling Effects 0.000 claims abstract description 149
- 238000010168 coupling process Methods 0.000 claims abstract description 149
- 238000005859 coupling reaction Methods 0.000 claims abstract description 149
- 238000012546 transfer Methods 0.000 claims description 12
- 230000007704 transition Effects 0.000 description 17
- 230000015654 memory Effects 0.000 description 9
- 238000009966 trimming Methods 0.000 description 8
- 238000004891 communication Methods 0.000 description 7
- 230000033001 locomotion Effects 0.000 description 6
- 230000036541 health Effects 0.000 description 4
- 230000007246 mechanism Effects 0.000 description 4
- 238000012544 monitoring process Methods 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000010276 construction Methods 0.000 description 3
- 230000004044 response Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000005355 Hall effect Effects 0.000 description 1
- 238000003491 array Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
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- 239000004065 semiconductor Substances 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H19/00—Gearings comprising essentially only toothed gears or friction members and not capable of conveying indefinitely-continuing rotary motion
- F16H19/08—Gearings comprising essentially only toothed gears or friction members and not capable of conveying indefinitely-continuing rotary motion for interconverting rotary motion and oscillating motion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H37/00—Combinations of mechanical gearings, not provided for in groups F16H1/00 - F16H35/00
- F16H37/02—Combinations of mechanical gearings, not provided for in groups F16H1/00 - F16H35/00 comprising essentially only toothed or friction gearings
- F16H37/04—Combinations of toothed gearings only
- F16H37/041—Combinations of toothed gearings only for conveying rotary motion with constant gear ratio
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
- B64C13/505—Transmitting means with power amplification using electrical energy having duplication or stand-by provisions
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/24—Operating mechanisms electric
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automation & Control Theory (AREA)
- Transmission Devices (AREA)
- Structure Of Transmissions (AREA)
Abstract
A redundant load transmission comprising: an input shaft configured to receive rotational torque from a primary drive; an output shaft configured to transmit rotational torque to the actuator; and a coupling assembly configured to connect the input shaft to the output shaft to transmit rotational torque. The input shaft is configured to receive rotational torque from the primary drive and transmit rotational torque through the coupling assembly when the coupling assembly is in the primary drive configuration. The coupling assembly is configured to disconnect from the input shaft and transmit rotational torque from the auxiliary drive to the output shaft when the coupling assembly is in the auxiliary drive configuration.
Description
Cross Reference to Related Applications
The present application claims the benefit of U.S. provisional application No.63/128,336, filed on 21 month 12 2020, which is hereby incorporated by reference in its entirety for all purposes as if fully set forth herein.
Technical Field
The present disclosure relates to a transmission for an actuator. More particularly, the present disclosure relates to a redundant load transmission and method for an actuator. The present disclosure further relates to a redundant drive system and method for an actuator.
Background
Electromechanical actuators are well known in the automotive industry, the aerospace industry, and other industries. The actuator typically has only a single drive system and may not actuate properly during a mechanical failure. Actuator failure in critical applications is highly undesirable and can present significant safety issues as well as potentially serious damage to equipment.
For example, one application of electromechanical actuators is in landing gear systems on aircraft. The landing gear system of an aircraft must be reliably deployed from a stowed position to an extended position during landing. In some arrangements, the landing gear is deployed by rotating about a pivot in response to operation of an actuator, such as an electromechanical linear actuator.
In the event of a mechanical failure within the actuator, the landing gear actuator will typically fail to deploy. In particular, many landing gear actuators have only a single drive system and may not properly deploy during a mechanical failure of the single drive system. For example, a single drive system may jam during a fault, thereby preventing further movement of the transmission and actuator. Landing gear actuator failure is highly undesirable and can present significant safety issues and the possibility of serious aircraft damage.
It would therefore be desirable to have an actuator with a redundant system to overcome mechanical failure and improve safety and limit equipment damage.
Disclosure of Invention
The above needs are met, to a great extent, by the present disclosure, which describes a redundant load transmission for an actuator. In one aspect, the actuator may be configured to actuate and extend the landing gear of the aircraft. In one aspect, the actuator may be configured to actuate a flight surface of an aircraft. In one aspect, the actuator may be configured to actuate a flight surface of an aircraft, the flight surface comprising one of: ailerons, elevators, leading edge flaps, leading edge slots, ground spoilers, inboard flaps, inboard ailerons, inboard aileron flaps, outboard flaps, balancing flaps, outboard ailerons, flight spoilers, trimming flaps, slats, air brakes, elevator trimming, control horns, rudder trimming, aileron trimming, and the like. In one aspect, the actuator may be configured to actuate a component of an aircraft, such as a thrust reverser, a weapon system, an in-flight fueling system, a tail hook grasping system, and/or the like.
One aspect includes a redundant load transmission, the redundant load transmission comprising: an input shaft configured to receive rotational torque from a primary drive; an output shaft configured to transmit the rotational torque to an actuator; a coupling assembly configured to connect the input shaft to the output shaft to transfer the rotational torque; the input shaft is configured to receive the rotational torque from the primary drive and transmit the rotational torque through the coupling assembly when the coupling assembly is in a primary drive configuration; and the coupling assembly is configured to disconnect from the input shaft and transfer rotational torque from the auxiliary drive to the output shaft when the coupling assembly is in the auxiliary drive configuration.
In one aspect, a redundant load transmission includes: an input shaft configured to receive rotational torque from a primary drive; an output shaft configured to transmit the rotational torque to an actuator; a coupling assembly configured to connect the input shaft to the output shaft to transfer the rotational torque; the input shaft is configured to receive the rotational torque from the primary drive and transmit the rotational torque through the coupling assembly when the coupling assembly is in a primary drive configuration; and the coupling assembly is configured to disconnect from the input shaft and transfer rotational torque from the auxiliary drive to the output shaft when the coupling assembly is in the auxiliary drive configuration.
In one aspect, the redundant load transmission may further include an emergency controller. The emergency controller may be implemented by hardware as described herein. In this regard, the redundant load transmission may be activated by applying power to the emergency controller. In one aspect, the redundant load transmission may be configured to operate in a normal mode and further configured to implement health monitoring. The health monitoring may be implemented by hardware as described herein.
In one aspect, the redundant load transmission may further include: a controller in electrical communication with the primary drive and the secondary drive; and a sensor configured to send a signal to the controller when the primary drive configuration has failed. The controller may be configured to switch the redundant load transmission from the primary drive configuration to the secondary drive configuration in response to receiving the signal from the sensor. A landing gear system may include the redundant load transmission described above, wherein the actuator may include a landing gear actuator configured to extend and retract the landing gear.
There has thus been outlined, rather broadly, certain aspects of the disclosure in order that the detailed description thereof herein may be better understood, and in order that the present contribution to the art may be better appreciated. There are, of course, additional aspects of the disclosure that will be described hereinafter and which will form the subject matter of the claims appended hereto.
In this regard, before explaining at least one aspect of the disclosure in detail, it is to be understood that the disclosure is not limited in its application to the details of construction and to the arrangements of the components set forth in the following description or illustrated in the drawings. The disclosure is capable of embodiments in addition to those described and of being practiced and carried out in various ways. Further, it is to be understood that the phraseology and terminology employed herein, as well as the abstract, are for the purpose of description and should not be regarded as limiting.
As such, those skilled in the art will appreciate that the conception upon which this disclosure is based may readily be utilized as a basis for the designing of other structures, methods and systems for carrying out the several purposes of the present disclosure. It is important, therefore, that the claims be regarded as including such equivalent constructions insofar as they do not depart from the spirit and scope of the present disclosure.
Drawings
Fig. 1 illustrates a schematic diagram of an actuator system in accordance with an aspect of the present disclosure.
Fig. 2A illustrates an end view of a redundant load transmission in accordance with an aspect of the present disclosure.
Fig. 2B illustrates a cross-sectional view of the redundant load transmission according to fig. 2A.
Fig. 3 illustrates an exploded view of a portion of a redundant load transmission according to an aspect of the present disclosure.
Detailed Description
The present disclosure will now be described with reference to the drawings, wherein like reference numerals refer to like parts throughout. Aspects of the present disclosure advantageously provide a transmission that provides redundant drive for an actuator.
Fig. 1 illustrates a schematic diagram of an actuator system in accordance with an aspect of the present disclosure.
The actuator system 101 may include a redundant load transmission 100 that may be connected to a primary drive 150 for driving the actuator 154 in a primary drive configuration. In this regard, rotation of primary drive 150 may generate torque that is applied to redundant load transmission 100 through input shaft 104. The redundant load transmission 100 may then output torque to the actuator 154 to operate the actuator 154 via the output shaft 112.
The redundant load transmission 100 may be configured to disconnect from the primary drive 150 when the primary drive 150 fails. In one aspect, the disconnection of primary drive 150 from redundant load transmission 100 may be to ensure continued operation of redundant load transmission 100 and actuator 154. In this regard, the failure of primary drive 150 may include a failure to prevent further rotation of the drive shaft or other components of primary drive 150. For example, primary drive 150 may jam. This type of failure will result in the transmission not being able to rotate and the actuator 154 not being able to actuate.
Thus, decoupling the primary drive 150 from the redundant load transmission 100 may prevent the redundant load transmission 100 from being rotationally locked based on failure of the primary drive 150 to rotate. Accordingly, the redundant load transmission 100 may be disconnected from the primary drive motor, and thereafter, the redundant load transmission 100 may be driven by the secondary drive 152 through the input shaft 136, which in turn drives the actuator 154 through the output shaft 112.
The actuator 154 may be configured to actuate any type of automobile, aircraft, and/or similar type of component. In one aspect, the actuator 154 may be configured to actuate and extend the landing gear of the aircraft. In one aspect, the actuator 154 may be configured to actuate a flight surface of an aircraft. In one aspect, the actuator 154 may be configured to actuate a flight surface of the aircraft, the flight surface including one of: ailerons, elevators, leading edge flaps, leading edge slots, ground spoilers, inboard flaps, inboard ailerons, inboard aileron flaps, outboard flaps, balancing flaps, outboard ailerons, flight spoilers, trimming flaps, slats, air brakes, elevator trimming, control horns, rudder trimming, aileron trimming, and the like. In one aspect, the actuator 154 may be configured to actuate a component of the aircraft, such as a thrust reverser, a weapon system, an in-flight fueling system, a tail hook grasping system, or the like.
Fig. 2A illustrates an end view of a redundant load transmission in accordance with an aspect of the present disclosure.
Fig. 2B illustrates a cross-sectional view of the redundant load transmission according to fig. 2A.
The redundant load transmission 100 may include a primary drive system 200. In aspects, the primary drive system 200 may include a primary coupling 102 driven by the input shaft 104 of the primary drive 150. The primary coupling 102 may have gears or other driven devices as well as splines or other devices that couple the primary coupling 102 to the output shaft 112.
In particular, the primary coupling 102 may have gear teeth on its outer diameter, as illustrated in fig. 2A. The gear teeth of the primary coupling 102 may engage the gear teeth on the input shaft 104. Additionally, the primary coupling 102 may include splines on its inner diameter. The splines of the primary coupling 102 may engage corresponding splines on the output shaft 112.
The output shaft 112 may be controlled and bearings 126 or other means may be used to provide axial support. The output shaft 112 may utilize thrust bearings 115 to provide a means of transmitting tension and compression loads to a grounded member, such as a housing. The thrust bearing 115 may also be used to isolate rotation in the primary load path so that only the intended components of the redundant load drive 100 may be allowed to rotate. The primary drive system 200 may include a spring or other member that exerts a force between the output shaft 112 and the primary coupling 102 to maintain a position that aligns the input shaft 104, primary coupling 102, and output shaft 112.
Redundant load transmission 100 includes an emergency drive system 202. Emergency drive system 202 may include auxiliary drive coupling 120 driven by auxiliary drive 152 and auxiliary shaft 116. The auxiliary drive coupling 120 may have gears or other driven devices and splines or other devices that couple the auxiliary drive coupling 120 to the output shaft 112.
In particular, the auxiliary drive coupling 120 may have gear teeth on its outer diameter. The gear teeth of the auxiliary drive coupling 120 may engage the gear teeth on the input shaft 136. Additionally, the auxiliary drive coupling 120 may include splines on its inner diameter. The splines of the auxiliary drive coupling 120 may engage corresponding splines on the output shaft 112.
The auxiliary drive coupling 120 may remain in the stowed position unless acted upon by the auxiliary drive 152. When commanded, the auxiliary drive 152 rotates the auxiliary shaft 116 and, in turn, the auxiliary drive coupling 120.
The transition from the primary drive 150 to the secondary drive 152 may include a transition mechanism 31 and/or a linear drive mechanism to translate the secondary drive 152 onto the output shaft 112 and move the primary drive system 200 out of engagement with the output shaft 112, the transition mechanism 31 utilizing a transition coupling 118 that may include a helical gear or other device when commanded.
When a transition from primary drive 150 to secondary drive 152 occurs, secondary drive coupling 120 is driven to actuate and may compress one or more springs 130. In various aspects, one or more springs 130 may be disposed between the output shaft 112 and the primary coupling 102. During the transition, the primary coupling 102 may be driven off of the splines or other coupling means of the output shaft 112, while the secondary drive coupling 120 transitions onto the output shaft 112. When the linear transition from primary drive 150 to secondary drive 152 has been completed, redundant load transmission 100 may begin transmitting torque to output shaft 112.
Fig. 3 illustrates an exploded view of a portion of a redundant load transmission according to an aspect of the present disclosure.
In particular, FIG. 3 illustrates components of an embodiment for providing transition of the auxiliary drive 152 from the primary drive 150. The transition mechanism 31 may include a grounded housing, a transition coupling 118, which may have gear teeth or other means to allow the transition coupling 118 to be driven, and an auxiliary drive coupling 120. When commanded, the transition coupling 118 may be driven by an input shaft 136, which may be implemented as a transition shaft, which, as illustrated, may rotate and translate the assembly in the direction of the primary drive system 200. The linear movement of the transition coupling 118 may move the auxiliary drive coupling 120 (which in this example is clamped on both sides by the thrust bearings 115), the primary coupling 102 away from the splines of the output shaft 112 or equivalent connection structure, compressing the springs 130 as the auxiliary drive coupling 120 transitions onto the splines of the output shaft 112. In this example, the thrust bearing 115 may ensure that only linear motion is the only force used to transition from the primary drive 150 to the secondary drive 152.
The redundant load transmission 100 may implement a controller. In one aspect, the redundant load transmission 100 may be implemented as an emergency controller. The emergency controller may be implemented by hardware as described herein. In this regard, the redundant load transmission 100 may be activated by applying power to the emergency controller. In one aspect, the redundant load transmission may be configured to operate in a normal mode and further configured to implement health monitoring. The health monitoring may be implemented by hardware as described herein. The controller may include a processor configured to execute instructions stored on a computer readable medium.
In a particular aspect, the controller may be configured to control the operation of the primary drive 150, the secondary drive 152, and the redundant load transmission 100 during primary configuration operations and/or secondary configuration operations. In particular, the controller may control the operation of the redundant load drive 100 to change from the primary configuration to the secondary configuration.
In one aspect, a processor implements the process described below. The instructions may include various commands for controlling the components of the redundant load drive 100. The computer readable medium may be any type of memory known in the art, including non-volatile memory, such as magnetic fixed disk storage, cloud-based memory, flash memory, and the like. The processor may also communicate with other types of memory including random access memory and read only memory. The controller may also include a display that may show various states and indications associated with instructions executed by the processor. For example, the display may display the failure of primary drive 150 and the implementation of the secondary configuration.
The controller may be in communication with a plurality of input devices and output devices. The plurality of input devices may include a user interface device such as a keyboard, mouse, or other peripheral device to receive user input. The user input may include initiation of an auxiliary configuration.
The plurality of input devices may also include sensors in communication with various components of the redundant load drive 100, such as motion sensors, speed sensors, voltage sensors, current sensors, or other detection devices known in the art. In particular, the sensors may include sensors for determining a failure of primary drive 150.
The plurality of output devices may include various electrical and/or mechanical control devices, such as switches, electrical and/or electromechanical relays, actuators, or other components known in the art, that may be used to control the various components of the redundant load transmission 100. In particular, the output device may control the redundant transmission to switch from the primary configuration to the secondary configuration.
The controller may receive signals from the primary drive system 200 and/or the primary drive 150 that sense the operation of components associated with the primary drive system 200. The controller may also receive signals from the redundant load drive 100 that sense operation of the redundant load drive 100, particularly the input shaft 104 and/or the output shaft 112. For example, the redundant load transmission 100 may be capable of detecting movement of the input shaft 104 and/or the output shaft 112 via a sensor, such as a hall effect sensor. In other aspects, sensors may be used to detect movement of the input shaft 104 and/or the output shaft 112. In other aspects, sensors may be used to detect failure of primary drive 150.
The controller may determine whether the primary drive system 200 and/or the redundant load transmission 100 are operating properly. If the controller does not sense any problems with the primary drive system 200, the primary drive 150, and/or the redundant load transmission 100, the primary drive system 200 may continue to provide torque to the input shaft 104. The controller may continue to receive signals from the primary drive system 200 regarding the operation of the redundant load transmission 100.
In some cases, the controller may detect problems in the operation of the primary drive system 200, the primary drive 150, and/or the redundant load transmission 100. For example, a failure within primary drive system 200 or primary drive 150 may cause redundant load transmission 100 to seize or remain stationary. As a result, the input shaft 104 and/or the output shaft 112 may lock and not function properly. When a fault has been detected, a controller operatively coupled to the redundant load transmission 100 may send a signal to the auxiliary drive 152 to initiate the auxiliary drive mode.
The controller may signal the flight warning system to notify the primary drive system 200 of the failure. For example, a warning message may be sent to the pilot that auxiliary drive system 116 has been engaged. The pilot may be notified via a display or another output device in communication with the controller. The controller may provide additional diagnostic information related to the fault to the user based on information received from the various input devices. For example, the controller may notify the user of the type of failure that causes switching to the auxiliary drive mode.
Thus, the described actuator system 101 is configured to implement a redundant system in order to overcome mechanical failure and improve safety and limit equipment damage. In particular, the actuator system 101 may determine a fault in the primary drive 150, disconnect the primary drive 150 from the redundant load transmission 100, and implement the secondary drive 152 to actuate the actuator 154.
The following are a number of non-limiting examples of aspects of the present disclosure. The following are a number of non-limiting examples of aspects of the present disclosure. One example includes: example 1. A redundant load transmission includes: an input shaft configured to receive rotational torque from a primary drive; an output shaft configured to transmit the rotational torque to an actuator; a coupling assembly configured to connect the input shaft to the output shaft to transfer the rotational torque; the input shaft is configured to receive the rotational torque from the primary drive and transmit the rotational torque through the coupling assembly when the coupling assembly is in a primary drive configuration; and the coupling assembly is configured to disconnect from the input shaft and transfer rotational torque from the auxiliary drive to the output shaft when the coupling assembly is in the auxiliary drive configuration.
The above examples may further include any one or a combination of more than one of the following examples: 2. a redundant load transmission according to any example herein wherein the coupling assembly comprises an auxiliary drive coupling configured to be driven by the auxiliary drive and auxiliary shaft. 3. A redundant load transmission according to any one of the examples herein wherein the coupling assembly is configured to disengage from the input shaft by translating the coupling assembly along the output shaft away from the input shaft. 4. A redundant load transmission according to any of the examples herein wherein the coupling assembly is configured to translate away from the input shaft when the redundant load transmission changes from the primary drive configuration to the secondary drive configuration. 5. A redundant load transmission according to any example herein wherein the auxiliary drive is configured to rotate the auxiliary shaft and thereby the auxiliary drive coupling. 6. A redundant load transmission according to any one of the examples herein wherein the coupling assembly is configured to disengage from the input shaft by translating the coupling assembly along the output shaft away from the input shaft. 7. A redundant load transmission according to any of the examples herein wherein the coupling assembly is configured to translate away from the input shaft when the redundant load transmission changes from the primary drive configuration to the secondary drive configuration. 8. A redundant load transmission according to any one of the examples herein wherein the coupling assembly is configured to disengage from the input shaft by translating the coupling assembly along the output shaft away from the input shaft. 9. A redundant load transmission according to any of the examples herein wherein the coupling assembly is configured to translate away from the input shaft when the redundant load transmission changes from the primary drive configuration to the secondary drive configuration. 10. A redundant load drive according to any example herein wherein the coupling assembly is configured to disengage from the input shaft by translating the coupling assembly along the output shaft away from the input shaft; and wherein the coupling assembly is configured to translate away from the input shaft when the redundant load transmission changes from the primary drive configuration to the secondary drive configuration. 11. A landing gear system comprising a redundant load transmission according to any of the examples herein, wherein the actuator comprises a landing gear actuator configured to extend and retract the landing gear.
One example includes: example 1. A redundant load transmission includes: an input shaft configured to receive rotational torque from a primary drive; an output shaft configured to transmit the rotational torque to an actuator; a coupling assembly configured to connect the input shaft to the output shaft to transfer the rotational torque; the input shaft is configured to receive the rotational torque from the primary drive and transmit the rotational torque through the coupling assembly when the coupling assembly is in a primary drive configuration; and the coupling assembly is configured to disconnect from the input shaft and transfer rotational torque from the auxiliary drive to the output shaft when the coupling assembly is in the auxiliary drive configuration.
The above examples may further include any one or a combination of more than one of the following examples: 2. a redundant load transmission according to any one of the examples herein wherein the coupling assembly is configured to disengage from the input shaft by translating the coupling assembly along the output shaft away from the input shaft. 3. A redundant load transmission according to any one of the examples herein wherein the coupling assembly comprises an inner coupling portion and an outer coupling portion; wherein the outer coupling portion comprises a helical gear surface; and wherein the helical gear surface is configured to be engaged by a drive gear and translated by rotation of the drive gear to disengage the coupling assembly from the input shaft in the auxiliary drive configuration. 4. A redundant load transmission according to any of the examples herein wherein the drive gear is configured to be rotated by the auxiliary drive. 5. A redundant load drive according to any example herein wherein the outer coupling portion is configured to receive the inner coupling portion. 6. A redundant load transmission according to any of the examples herein wherein the coupling assembly is configured to translate away from the input shaft when the redundant load transmission changes from the primary drive configuration to the secondary drive configuration. 7. A redundant load transmission according to any of the examples herein comprising a spring arrangement around the output shaft, wherein the coupling assembly is further configured to compress the spring when the redundant load transmission is changed from the primary drive configuration to the secondary drive configuration. 8. A redundant load transmission according to any one of the examples herein wherein the coupling assembly further comprises a bearing, wherein the bearing is configured to compress the spring when the redundant load transmission is changed from the primary drive configuration to the secondary drive configuration. 9. A redundant load drive according to any example herein wherein the input shaft comprises input shaft splines; wherein the coupling assembly includes an inner coupling spline configured to engage the input shaft spline of the input shaft; and wherein the output shaft includes an output shaft spline configured to engage the inner coupling spline of the coupling assembly. 10. A redundant load drive according to any example herein wherein the coupling assembly is configured to disengage the inner coupling spline from the input shaft spline of the input shaft by translating the coupling assembly along the output shaft away from the input shaft. 11. A redundant load transmission according to any one of the examples herein wherein the coupling assembly comprises an inner coupling portion and an outer coupling portion; wherein the outer coupling portion comprises a helical gear surface; and wherein the helical gear surface is configured to be engaged by a drive gear and translated by rotation of the drive gear to disengage the inner coupling spline of the coupling assembly from the input shaft spline of the input shaft in the auxiliary drive configuration. 12. A redundant load transmission according to any one of the examples herein wherein the coupling assembly comprises an inner coupling portion and an outer coupling portion; and wherein the outer coupling portion is configured to engage the inner coupling portion in the auxiliary drive configuration to disengage from the input shaft by translating the coupling assembly along the output shaft away from the input shaft. 13. A redundant load transmission according to any one of the examples herein wherein the coupling assembly comprises an inner coupling portion and an outer coupling portion; wherein the outer coupling portion comprises teeth; wherein the inner coupling portion comprises teeth; and wherein the outer coupling portion is configured to engage the teeth of the inner coupling portion in the auxiliary drive configuration to disengage the coupling assembly from the input shaft by translating the coupling assembly along the output shaft away from the input shaft. 14. A redundant load drive as described in any of the examples herein comprising: a controller in electrical communication with the primary drive and the secondary drive; and a sensor configured to send a signal to the controller when the primary drive configuration has failed. 15. A redundant load transmission according to any example herein wherein the controller is configured to switch the redundant load transmission from the primary drive configuration to the secondary drive configuration in response to receiving the signal from the sensor. 16. A landing gear system comprising a redundant load transmission according to any of the examples herein, wherein the actuator comprises a landing gear actuator configured to extend and retract the landing gear.
One example includes: example 17 a redundant load transmission includes: an input shaft configured to receive rotational torque from a primary drive; an output shaft configured to transmit the rotational torque to an actuator; a coupling assembly configured to connect the input shaft to the output shaft to transfer the rotational torque; the input shaft is configured to receive the rotational torque from the primary drive and transmit the rotational torque through the coupling assembly when the coupling assembly is in a primary drive configuration; the coupling assembly is configured to disconnect from the input shaft and transfer rotational torque from the auxiliary drive to the output shaft when the coupling assembly is in the auxiliary drive configuration; a controller in electrical communication with the primary drive and the secondary drive; and a sensor configured to send a signal to the controller when the primary drive configuration has failed.
The above examples may further include any one or a combination of more than one of the following examples: 18. a redundant load drive according to any example herein wherein the input shaft comprises input shaft splines; wherein the coupling assembly includes an inner coupling spline configured to engage the input shaft spline of the input shaft; and wherein the output shaft includes an output shaft spline configured to engage the inner coupling spline of the coupling assembly. 19. A redundant load drive according to any example herein wherein the coupling assembly is configured to disengage the inner coupling spline from the input shaft spline of the input shaft by translating the coupling assembly along the output shaft away from the input shaft. 20. A redundant load transmission according to any one of the examples herein wherein the coupling assembly comprises an inner coupling portion and an outer coupling portion; wherein the outer coupling portion comprises a helical gear surface; and wherein the helical gear surface is configured to be engaged by a drive gear and translated by rotation of the drive gear to disengage the inner coupling spline of the coupling assembly from the input shaft spline of the input shaft in the auxiliary drive configuration.
Aspects of the present disclosure may be implemented in any type of computing device having the capability to communicate wired/wireless via a communication channel, such as desktop computers, personal computers, laptop/mobile computers, personal Data Assistants (PDAs), mobile telephones, tablet computers, cloud computing devices, and the like.
Further in accordance with various aspects of the present disclosure, the methods described herein are intended to operate with dedicated hardware implementations including, but not limited to, PCs, PDAs, semiconductors, application Specific Integrated Circuits (ASICs), programmable logic arrays, cloud computing devices, and other hardware devices configured to implement the methods described herein.
It should also be noted that software implementations of the disclosure as described herein may alternatively be stored on a tangible storage medium, such as: magnetic media such as magnetic disks or tapes; magneto-optical or optical media such as magnetic disks; or a solid state medium such as a memory card or other package housing one or more read-only (non-volatile) memories, random access memories, or other re-writable (volatile) memories. Digital file attachments to e-mail or other independent information files or archive sets are considered to be distribution media equivalent to tangible storage media. Accordingly, the present disclosure is considered to include a tangible storage medium or distribution medium as set forth herein and including art-recognized equivalents and successor media, in which the software embodiments herein are stored.
Additionally, various aspects of the disclosure may be implemented in non-general purpose computer implementations. Further, the various aspects of the disclosure set forth herein improve the functionality of the system as is apparent from the disclosure thereof. Furthermore, various aspects of the present disclosure relate to computer hardware that is specifically programmed to address the complex problems addressed by the present disclosure. Accordingly, various aspects of the present disclosure generally improve the functionality of the system in particular embodiments of the system to perform the processes set forth in the present disclosure and defined by the claims.
The many features and advantages of the present disclosure are apparent from the detailed specification and, thus, it is intended by the appended claims to cover all such features and advantages of the disclosure which fall within the true spirit and scope of the disclosure. Further, since numerous modifications and changes will readily occur to those skilled in the art, it is not desired to limit the disclosure to the exact construction and operation illustrated and described, and accordingly, all suitable modifications and equivalents may be resorted to, falling within the scope of the disclosure.
Claims (11)
1. A redundant load transmission comprising:
an input shaft configured to receive rotational torque from a primary drive;
an output shaft configured to transmit the rotational torque to an actuator;
a coupling assembly configured to connect the input shaft to the output shaft to transfer the rotational torque;
the input shaft is configured to receive the rotational torque from the primary drive and transmit the rotational torque through the coupling assembly when the coupling assembly is in a primary drive configuration; and is also provided with
The coupling assembly is configured to disconnect from the input shaft and transfer rotational torque from the auxiliary drive to the output shaft when the coupling assembly is in the auxiliary drive configuration.
2. The redundant load transmission of claim 1 wherein the coupling assembly comprises an auxiliary drive coupler configured to be driven by the auxiliary drive and auxiliary shaft.
3. The redundant load transmission of claim 2,
wherein the coupling assembly is configured to disengage from the input shaft by translating the coupling assembly along the output shaft away from the input shaft.
4. The redundant load transmission of claim 2,
wherein the coupling assembly is configured to translate away from the input shaft when the redundant load transmission changes from the primary drive configuration to the secondary drive configuration.
5. A redundant load transmission as claimed in claim 2, wherein the auxiliary drive is configured to rotate the auxiliary shaft and thereby the auxiliary drive coupling.
6. The redundant load transmission of claim 5,
wherein the coupling assembly is configured to disengage from the input shaft by translating the coupling assembly along the output shaft away from the input shaft.
7. The redundant load transmission of claim 5,
wherein the coupling assembly is configured to translate away from the input shaft when the redundant load transmission changes from the primary drive configuration to the secondary drive configuration.
8. The redundant load transmission of claim 1,
wherein the coupling assembly is configured to disengage from the input shaft by translating the coupling assembly along the output shaft away from the input shaft.
9. The redundant load transmission of claim 1,
wherein the coupling assembly is configured to translate away from the input shaft when the redundant load transmission changes from the primary drive configuration to the secondary drive configuration.
10. The redundant load transmission of claim 1,
wherein the coupling assembly is configured to disengage from the input shaft by translating the coupling assembly along the output shaft away from the input shaft; and is also provided with
Wherein the coupling assembly is configured to translate away from the input shaft when the redundant load transmission changes from the primary drive configuration to the secondary drive configuration.
11. A landing gear system comprising a redundant load transmission according to claim 1, wherein the actuator comprises a landing gear actuator configured to extend and retract the landing gear.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US202063128336P | 2020-12-21 | 2020-12-21 | |
| US63/128,336 | 2020-12-21 | ||
| PCT/US2021/064728 WO2022140466A1 (en) | 2020-12-21 | 2021-12-21 | Dual drive redundant load transmission device and process |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116745546A true CN116745546A (en) | 2023-09-12 |
Family
ID=82160092
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202180087788.2A Pending CN116745546A (en) | 2020-12-21 | 2021-12-21 | Dual drive redundant load transmission and method |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US11662001B2 (en) |
| EP (1) | EP4264086A1 (en) |
| JP (1) | JP2024501992A (en) |
| CN (1) | CN116745546A (en) |
| CA (1) | CA3202809A1 (en) |
| WO (1) | WO2022140466A1 (en) |
Family Cites Families (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3304487C1 (en) * | 1983-02-10 | 1984-03-01 | Werner Kring - Konstruktionsbüro, 6342 Haiger | Actuator |
| DE3335858A1 (en) * | 1983-10-03 | 1985-04-18 | SMS Schloemann-Siemag AG, 4000 Düsseldorf | DEVICE FOR THE HORIZONTAL ADJUSTMENT OF INSTALLATION PIECES IN ROLLING MILLS |
| US4637272A (en) | 1985-10-28 | 1987-01-20 | Sundstrand Corporation | Ballscrew actuator |
| US4858490A (en) | 1987-10-13 | 1989-08-22 | Hughes Aircraft Company | Two motor redundant drive mechanism |
| DE3817651A1 (en) | 1988-05-25 | 1989-12-07 | Messerschmitt Boelkow Blohm | REDUNDANT DRIVE DEVICE |
| US6082207A (en) * | 1996-09-06 | 2000-07-04 | Thomson Saginaw Ball Screw Company, L.L.C. | Vertically operating ball screw and nut actuator system for synchronously moving multiple elements in load balanced opposed directions, and methods of constructing and operating ball screw actuator systems |
| DE29919877U1 (en) * | 1999-11-11 | 2001-03-15 | Dewert Antriebs Systemtech | Electromotive adjustment device |
| US6405782B1 (en) * | 2000-11-16 | 2002-06-18 | Keng Mu Cheng | Transmission system for a motor-driven blind |
| FR2840377B1 (en) | 2002-05-31 | 2004-09-03 | Messier Bugatti | TWO-MOTOR ACTUATOR, DIFFERENTIAL REDUCER AND TORQUE LIMITER |
| US8230750B2 (en) * | 2006-09-01 | 2012-07-31 | Parker-Hannifin Corporation | Electromechanical actuating assembly |
| US8070094B2 (en) | 2008-07-16 | 2011-12-06 | Hamilton Sundstrand Corporation | Aircraft landing gear actuator |
| US20130283948A1 (en) * | 2012-04-27 | 2013-10-31 | Hsin Hao Health Materials Co., Ltd. | Massage apparatus |
| TWM478082U (en) * | 2014-01-22 | 2014-05-11 | Timotion Technology Co Ltd | Linear actuating device |
| DE102014210253B4 (en) * | 2014-05-28 | 2016-02-11 | Aktiebolaget Skf | Transmission for a height-adjustable shelf and method for changing a height of a shelf |
-
2021
- 2021-12-21 CN CN202180087788.2A patent/CN116745546A/en active Pending
- 2021-12-21 WO PCT/US2021/064728 patent/WO2022140466A1/en active Application Filing
- 2021-12-21 JP JP2023539376A patent/JP2024501992A/en active Pending
- 2021-12-21 CA CA3202809A patent/CA3202809A1/en active Pending
- 2021-12-21 US US17/558,487 patent/US11662001B2/en active Active
- 2021-12-21 EP EP21912091.2A patent/EP4264086A1/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| JP2024501992A (en) | 2024-01-17 |
| US11662001B2 (en) | 2023-05-30 |
| CA3202809A1 (en) | 2022-06-30 |
| EP4264086A1 (en) | 2023-10-25 |
| WO2022140466A1 (en) | 2022-06-30 |
| US20220235853A1 (en) | 2022-07-28 |
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